M7373 L-CMC
C DATA LOADER OUTPUT
FMC
DATA LOADER OUTPUT A
A DATA LOADER OUTPUTM7443 R-FMC
ACARS/CMU
DATA LOADER INPUT
DATA LOADER INPUT
LOADER ENABLE
NDLOADER ENABLE
PFD B7077 L-FCC
B10222 CMUDATA LOADER OUTPUTA
DATA LOADER OUTPUT
EICAS
EIU DATA LOADER INPUT
DATA LOADER INPUTLOADER ENABLE
LOADER ENABLE
A DATA LOADER OUTPUTM7350 CAPT ND
M7353 L-EIU
FCC
CMC
DATA LOADER OUTPUTC
DATA LOADER INPUTLOADER ENABLE
DATA LOADER INPUT
NORMAL
M7348 CAPT PFDFMC
LOADER ENABLE
A DATA LOADER OUTPUT
M7374 R-CMC
DATA LOADER OUTPUTC
DATA LOADER INPUT
LOADER ENABLEDATA LOADER INPUT
C DATA LOADER OUTPUT M7346 AUX EICASLOADER ENABLE ND
DATA LOADER INPUT
DATA LOADER OUTPUT
B7079 R-FCC
B
LOADER ENABLE
DATA LOADER INPUT/
PFD
D
M7342 F/O ND
EICAS
DOWNLOADING
C DATA LOADER OUTPUTLOADER ENABLE
EIU
B00584 DMU
DATA LOADER INPUTDATA LOADER OUTPUTB
ACMS LOADER ENABLE
FCC
DATA LOADER INPUTCMC
C DATA LOADER OUTPUTM7347 F/O PFDLOADER ENABLE
DATA LOADER INPUTB8238 PFIDS
LOADER ENABLE
RECEIVERB
M7345 MAIN EICAS
TRANSMITTER
C DATA LOADER OUTPUTNORMAL LOADER ENABLE
ACMS
DATA LOADER INPUTB7443 CMU
LOADER ENABLE
DATA LOADER OUTPUT B PFIDS ACESS
B DATA LOADER OUTPUTM7351 R-EIUACESS
DATA LOADER INPUT DATA LOADER INPUT
LOADER ENABLE TCAS LOADER ENABLE
B8385 TCAS UNIT M7325 C-EIUDATA LOADER OUTPUTB B DATA LOADER OUTPUT
EIU DOWNLOADED DATA FOR
THE ACMS RECEIVER IS DATA LOADER INPUT
1
SATCOM DATA LOADER INPUTNOT TRANSFERRED THROUGH
LOADER ENABLETHE SELECTOR SWITCH
LOADER ENABLE FCC
B8307 SATCOM B7078 C-FCC
M7996 DATA LOADER CONTROL PANEL
Software Data Loader/Recorder
Figure 21
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34-61-00
ALL ú ú 28 Page 39 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
M48973
A
747-400
MAINTENANCE MANUAL
4. Control Display Unit (CDU) (Fig. 22)
____________________
A. General
(1)
The CDU provides the interface with the FMCS. It allows the operator to enter initialization data, reference data, and modifications in the flight plan. VHF NAV frequencies for manual tuning, as well as displaying pertinent information.
(2)
In addition to the above, the CDU also functions as an alternate EFIS/EICAS control panel in the case of primary EFIS control panel failure. It also provides alternate VHF NAV radio tuning in the case where the master FMC, defined by the master switch, has failed.
(3)
Other systems are also controlled through the CDU as well. These systems are CMC and ACMS and are selected via the MENU page which displays upon power up or by pressing the MENU function key.
(4)
There are three identical CDUs in the flight compartment. Only two of these CDUs (left and right) have bi-directional interfaces with the FMCs. The FMCs have an intersystem bus which allows for independent operation of each CDU.
(5)
This dual CDU operation in conjunction with the dual FMC operation enables failure survivability. If in the case of one FMC and one CDU failure the system will still be operational. Failure of one of the CDUs shall leave both the FMCs operational. Failure of one of the FMCs shall have both CDUs operational if the alternate port on the failed FMC is active.
(6)
Although three CDUs exist, only two will be applicable to the FMCS. The third CDU will be incorporated more into the CMS. The FMCs receive no input from the third CDU. The only applicable FMCS function the third CDU provides is the capability of manually tuning the center ILS and downloading the flight plan from the FMCs should the FMCs fail.
B. Physical Description (Fig. 23)
(1)
The CDU consists of metal chassis containing an electron tube assembly, a control module and a keyboard assembly. The electron tube assembly consists of a CRT, deflection yoke, amplifier and a high voltage power supply. The control module contains digital logic, memory, control circuitry and a low voltage power supply. The keyboard assembly incorporates panel mounting and provides a fold-down handle on the front panel for insertion and extraction from flight deck.
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